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assembly as on the removed balance panel assembly [24] or balance panel assembly [25].
(m) Install the balance weights [11] to the balance panel assembly with bolts [12].
1) Apply primer, C00259 to the holes of the balance weights [11].
2) Apply compound, C00528 to the bolts [12].
3) Tighten the bolt [12] to 35-40 pound-inches (4.0-5.0 newton-meters)..
(n) Install the seal retainers [27] on the aerodynamic seals [15] with the bolts [1] and [14].
SUBTASK 27-11-31-600-001
(3) Use a medium nylon bristle brush, STD-3911 to apply corrosion inhibiting compound, G00009 to
all edges of the seal retainers [18] and [27] and the interface between seal retainers [18] and [27]
and the seals [15], [20] and [29].
SUBTASK 27-11-31-410-001
(4) Install the applicable access panels on the lower wing surface at the aileron balance panel.
(a) For the left wing, close these access panels:
Number Name/Location
571BB Lower Outboard Fixed Trailing Edge Access Panel
571CB Lower Outboard Fixed Trailing Edge Access Panel
571DB Lower Outboard Fixed Trailing Edge Access Panel
(b) For the right wing, close these access panels:
Number Name/Location
671BB Lower Outboard Fixed Trailing Edge Access Panel
671CB Lower Outboard Fixed Trailing Edge Access Panel
671DB Lower Outboard Fixed Trailing Edge Access Panel
SUBTASK 27-11-31-860-002
(5) Do this task: Put the Aileron Hydraulic Systems A and B Back to the Condition Before
Pressure Removal, TASK 27-11-00-860-802.
SUBTASK 27-11-31-710-001
(6) Do this task: Aileron Travel Test, TASK 27-11-00-700-809.
------------------------- END OF TASK ---------------------------
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EFFECTIVITY
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D633A101-GUN
BOEING PROPRIETARY - Copyright#Unpublished Work - See title page for details
AILERON BALANCE PANEL - INSPECTION/CHECK
1. General
A. The procedure contains these tasks:
(1) A dimensional inspection of the aileron balance panel
(2) A visual inspection of the seals around the aileron balance panel.
TASK 27-11-31-220-801
2. Aileron Balance Panel Inspection
(Figure 601)
A. General
(1) This task gives wear limits and repair data for the aileron balance panel inspection.
B. References
Reference Title
27-11-31-000-801 Aileron Balance Panels Removal (P/B 401)
27-11-31-400-801 Aileron Balance Panels Installation (P/B 401)
C. Tools/Equipment
Reference Description
STD-1096 Micrometer - Depth, 0-1 Inch, Readable to 1/1000 Inch
STD-1097 Caliper - Vernier, 0-6 Inch, Readable to 1/1000 Inch
D. Location Zones
Zone Area
572 Left Wing - Aileron
672 Right Wing - Aileron
E. Procedure
SUBTASK 27-11-31-020-002
(1) Do this task: Aileron Balance Panels Removal, TASK 27-11-31-000-801.
SUBTASK 27-11-31-020-003
(2) Use these tools to do a check for wear on the parts of the aileron balance panel:
(a) micrometer (0-1 Inch, readable to 1/1000 Inch), STD-1096
(b) readable to 1/1000 inch vernier 0 - 6 inch caliper, STD-1097.
SUBTASK 27-11-31-020-004
(3) Examine the parts of the aileron balance panel for worn areas:
(a) Remove the parts you want to do a check.
(b) Measure the parts with a micrometer (0-1 Inch, readable to 1/1000 Inch), STD-1096 or a
readable to 1/1000 inch vernier 0 - 6 inch caliper, STD-1097.
(c) Compare the dimensions you measured with the permitted wear dimensions.
(d) If the parts are out of tolerance, replace or repair the part.
737-600/700/800/900
AIRCRAFT MAINTENANCE MANUAL
EFFECTIVITY
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Table 601/27-11-31-993-801
NAME OF THE PARTS
THAT ARE IN CONTACT
DIM.
DIAMETER DESIGN LIMITS WEAR LIMITS
MINIMUM
inches/mm
MAXIMUM
inches/mm
PERMITTED
MAXIMUM I.D./
MINIMUM O.D. OF
WORN PART
MAXIMUM
SERVICE
DIAMETRIC
CLEARANCE
#1 BUSHING I.D. 0.2500 in 0.2505 in 0.2515 in
6.3500 mm 6.3627 mm 6.3881 mm 0.0030 in
#1 BOLT O.D. 0.2485 in 0.2495 in 0.2475 in 0.0762 mm
6.3119 mm 6.3373 mm 6.2865 mm
#2 BUSHING I.D. 0.2505 in
6.3627 mm
0.2515 in
6.3881 mm
0.2525 in
6.4135 mm
0.0040 in
#2 BOLT O.D. 0.2485 in
6.3119 mm
0.2495 in
6.3373 mm
0.2475 in
6.2865 mm
0.1016 mm
#3 BUSHING I.D. 0.2500 in
6.3500 mm
0.2505 in
6.3627 mm
0.2515 in
6.3881 mm
0.0030 in
#3 BOLT O.D. 0.2485 in
6.3119 mm
0.2495 in
6.3373 mm
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737-600/700/800/900 AIRCRAFT MAINTENANCE MANUAL飞机维护手册1(153)
